XFOIL Version 6.96 Calculated polar for: NACA 4412 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.4048 0.09389 0.08857 -0.0483 1.0000 0.0478 -9.750 -0.4169 0.08955 0.08431 -0.0489 1.0000 0.0478 -9.500 -0.4366 0.08474 0.07959 -0.0495 1.0000 0.0479 -9.250 -0.4631 0.08006 0.07503 -0.0493 1.0000 0.0480 -8.750 -0.5253 0.06900 0.06415 -0.0511 1.0000 0.0479 -8.500 -0.5707 0.05119 0.04568 -0.0644 0.9952 0.0481 -8.250 -0.5467 0.04868 0.04308 -0.0673 0.9903 0.0493 -8.000 -0.5231 0.04492 0.03903 -0.0712 0.9851 0.0504 -7.750 -0.5018 0.04055 0.03419 -0.0746 0.9791 0.0518 -7.500 -0.4754 0.03665 0.02968 -0.0779 0.9741 0.0541 -7.250 -0.4503 0.03299 0.02525 -0.0800 0.9684 0.0562 -7.000 -0.4200 0.03096 0.02296 -0.0817 0.9634 0.0575 -6.750 -0.3850 0.02963 0.02147 -0.0840 0.9600 0.0593 -6.500 -0.3579 0.02848 0.02010 -0.0846 0.9527 0.0618 -6.250 -0.3232 0.02697 0.01822 -0.0865 0.9482 0.0647 -6.000 -0.2905 0.02560 0.01658 -0.0878 0.9431 0.0669 -5.750 -0.2604 0.02468 0.01563 -0.0886 0.9364 0.0692 -5.500 -0.2238 0.02383 0.01466 -0.0906 0.9323 0.0733 -5.250 -0.1930 0.02299 0.01359 -0.0913 0.9258 0.0776 -5.000 -0.1610 0.02221 0.01284 -0.0923 0.9197 0.0817 -4.750 -0.1239 0.02143 0.01196 -0.0942 0.9158 0.0879 -4.500 -0.0963 0.02085 0.01138 -0.0942 0.9078 0.0943 -4.250 -0.0626 0.02029 0.01069 -0.0953 0.9021 0.1036 -4.000 -0.0298 0.01972 0.01019 -0.0963 0.8963 0.1137 -3.750 -0.0012 0.01927 0.00975 -0.0965 0.8880 0.1252 -3.500 0.0341 0.01876 0.00925 -0.0979 0.8832 0.1405 -3.250 0.0601 0.01842 0.00895 -0.0975 0.8734 0.1560 -3.000 0.0943 0.01796 0.00851 -0.0985 0.8678 0.1762 -2.750 0.1208 0.01768 0.00826 -0.0982 0.8578 0.1966 -2.500 0.1543 0.01725 0.00791 -0.0991 0.8516 0.2223 -2.250 0.1807 0.01701 0.00771 -0.0986 0.8410 0.2480 -2.000 0.2125 0.01664 0.00739 -0.0992 0.8338 0.2786 -1.750 0.2399 0.01635 0.00720 -0.0989 0.8233 0.3107 -1.500 0.2689 0.01603 0.00700 -0.0990 0.8139 0.3511 -1.250 0.2984 0.01563 0.00678 -0.0991 0.8049 0.4075 -1.000 0.3243 0.01521 0.00672 -0.0985 0.7938 0.5006 -0.750 0.3496 0.01460 0.00664 -0.0973 0.7848 0.6595 -0.500 0.3752 0.01412 0.00663 -0.0954 0.7741 0.8453 -0.250 0.4266 0.01392 0.00639 -0.0997 0.7634 1.0000 0.000 0.4558 0.01393 0.00621 -0.0998 0.7530 1.0000 0.250 0.4826 0.01399 0.00614 -0.0994 0.7409 1.0000 0.500 0.5094 0.01407 0.00609 -0.0991 0.7289 1.0000 0.750 0.5371 0.01415 0.00604 -0.0988 0.7177 1.0000 1.000 0.5649 0.01424 0.00599 -0.0986 0.7065 1.0000 1.250 0.5909 0.01438 0.00605 -0.0982 0.6942 1.0000 1.500 0.6178 0.01451 0.00608 -0.0978 0.6828 1.0000 1.750 0.6455 0.01464 0.00609 -0.0976 0.6722 1.0000 2.000 0.6713 0.01482 0.00622 -0.0972 0.6603 1.0000 2.250 0.6976 0.01500 0.00633 -0.0968 0.6491 1.0000 2.500 0.7248 0.01517 0.00641 -0.0965 0.6390 1.0000 2.750 0.7505 0.01538 0.00659 -0.0960 0.6276 1.0000 3.000 0.7765 0.01560 0.00677 -0.0956 0.6169 1.0000 3.250 0.8035 0.01580 0.00689 -0.0953 0.6073 1.0000 3.500 0.8286 0.01605 0.00715 -0.0948 0.5961 1.0000 3.750 0.8545 0.01630 0.00737 -0.0943 0.5860 1.0000 4.000 0.8807 0.01654 0.00757 -0.0939 0.5762 1.0000 4.250 0.9054 0.01682 0.00787 -0.0933 0.5653 1.0000 4.500 0.9312 0.01709 0.00812 -0.0929 0.5556 1.0000 4.750 0.9563 0.01737 0.00842 -0.0923 0.5452 1.0000 5.000 0.9809 0.01768 0.00875 -0.0917 0.5348 1.0000 5.250 1.0066 0.01797 0.00902 -0.0913 0.5256 1.0000 5.500 1.0303 0.01830 0.00943 -0.0905 0.5147 1.0000 5.750 1.0545 0.01863 0.00979 -0.0899 0.5043 1.0000 6.000 1.0780 0.01893 0.01009 -0.0890 0.4918 1.0000 6.250 1.1002 0.01923 0.01038 -0.0879 0.4772 1.0000 6.500 1.1214 0.01955 0.01077 -0.0867 0.4620 1.0000 6.750 1.1425 0.01990 0.01117 -0.0855 0.4474 1.0000 7.000 1.1625 0.02025 0.01154 -0.0841 0.4307 1.0000 7.250 1.1810 0.02063 0.01193 -0.0825 0.4114 1.0000 7.500 1.1982 0.02105 0.01238 -0.0807 0.3902 1.0000 7.750 1.2150 0.02152 0.01285 -0.0788 0.3690 1.0000 8.000 1.2308 0.02205 0.01337 -0.0769 0.3473 1.0000 8.250 1.2453 0.02266 0.01398 -0.0748 0.3230 1.0000 8.500 1.2577 0.02337 0.01464 -0.0725 0.2970 1.0000 8.750 1.2668 0.02421 0.01539 -0.0697 0.2694 1.0000 9.000 1.2728 0.02520 0.01626 -0.0665 0.2418 1.0000 9.250 1.2779 0.02637 0.01732 -0.0635 0.2137 1.0000 9.500 1.2819 0.02769 0.01856 -0.0605 0.1872 1.0000 9.750 1.2847 0.02918 0.01994 -0.0577 0.1643 1.0000 10.000 1.2873 0.03077 0.02147 -0.0550 0.1449 1.0000 10.250 1.2892 0.03249 0.02314 -0.0525 0.1299 1.0000 10.500 1.2911 0.03429 0.02493 -0.0502 0.1182 1.0000 10.750 1.2917 0.03627 0.02689 -0.0480 0.1092 1.0000 11.000 1.2943 0.03819 0.02889 -0.0462 0.1015 1.0000 11.250 1.2947 0.04036 0.03108 -0.0444 0.0960 1.0000 11.500 1.2979 0.04238 0.03321 -0.0429 0.0905 1.0000 11.750 1.2980 0.04473 0.03559 -0.0415 0.0863 1.0000 12.000 1.3002 0.04698 0.03791 -0.0403 0.0824 1.0000 12.250 1.3033 0.04919 0.04024 -0.0392 0.0786 1.0000 12.500 1.3045 0.05162 0.04273 -0.0383 0.0756 1.0000 12.750 1.3053 0.05414 0.04526 -0.0373 0.0731 1.0000 13.000 1.3099 0.05635 0.04763 -0.0365 0.0702 1.0000 13.250 1.3130 0.05874 0.05013 -0.0358 0.0674 1.0000 13.500 1.3149 0.06128 0.05274 -0.0352 0.0650 1.0000 14.000 1.3213 0.06622 0.05785 -0.0341 0.0607 1.0000 14.250 1.3240 0.06885 0.06063 -0.0337 0.0584 1.0000 14.500 1.3262 0.07157 0.06345 -0.0335 0.0564 1.0000 14.750 1.3282 0.07428 0.06621 -0.0333 0.0546 1.0000 15.000 1.3308 0.07696 0.06893 -0.0330 0.0529 1.0000 15.250 1.3307 0.08019 0.07241 -0.0332 0.0511 1.0000 15.500 1.3304 0.08348 0.07587 -0.0334 0.0494 1.0000 15.750 1.3299 0.08678 0.07930 -0.0338 0.0478 1.0000 16.000 1.3299 0.09000 0.08258 -0.0343 0.0464 1.0000 16.250 1.3328 0.09267 0.08521 -0.0343 0.0450 1.0000 16.500 1.3257 0.09731 0.09017 -0.0356 0.0439 1.0000 16.750 1.3187 0.10199 0.09511 -0.0370 0.0427 1.0000